CN108860570A - A kind of foldable, fast assembling-disassembling unmanned airplane empennage and the unmanned plane including the empennage - Google Patents
A kind of foldable, fast assembling-disassembling unmanned airplane empennage and the unmanned plane including the empennage Download PDFInfo
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- CN108860570A CN108860570A CN201810464397.8A CN201810464397A CN108860570A CN 108860570 A CN108860570 A CN 108860570A CN 201810464397 A CN201810464397 A CN 201810464397A CN 108860570 A CN108860570 A CN 108860570A
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- empennage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a kind of foldable, fast assembling-disassembling unmanned airplane empennage and including the unmanned plane of the empennage.The empennage includes left and right two sections of empennages, the connection shaft for connecting two empennages and multiple connectors, and when work, left and right two sections of empennages can be launched into inverted " V " type tail layout around the shaft, fixed to keep configuration in the junction of left and right two sections of empennages；At the end of use, the connection of left and right empennage can be disconnected, the two folding is combined into one.It is equipped with connection structure in left and right two sections of empennage lower ends, is connected by the connection structure with shoe, to realize the connection of empennage and fuselage by shoe.This is foldable, fast assembling-disassembling empennage is easy to use, easy to operate, can realize Quick universal in outfield, because of its foldability, reduce the packing measurement(s) of complete machine, convenient transportation.
Description
Technical field
The present invention relates to a kind of foldable, fast assembling-disassembling unmanned airplane empennage and the unmanned plane including such empennage, belong to
Aviation aircraft technical field.
Background technique
Unmanned plane has been applied well in military domain, and with the maturation of technology, unmanned plane has progressed into civilian
Field, electric power, communication, meteorology, agricultural, ocean, the fields application such as exploration, photograph, prevent and reduce natural disasters technical effect and economy
Benefit is all very good.In addition, before unmanned plane also has good application in terms of enforcing the drug law anti-smuggling, border patrol, public security
Scape.Wherein fixed-wing unmanned plane is long with flying distance, cruise area is big, flying speed is fast, flying height is high, loading capacity is big,
It is suitble to the characteristics of working long hours at a distance, there is more extensive purposes in civil field.
In order to make each component simple installation of unmanned plane, easy to operate, Package size is small, convenient transportation, it is many at present nobody
Machine has been selected the way of each component segmentation of body.During selecting connection type, how to make it is easy to assembly quick,
The effective transmitting that can guarantee load again, improves the bearing capacity of each component, becomes the key of each member connection structure design.
The unmanned plane for using inverted " V " empennage at present, there is following several inverted " V " tail structures and mounting means：1. using whole
The disadvantages of body inverted " V " empennage, that there are packaging volumes is big for this empennage, and transport is inconvenient, installation is complicated；2. using shoe pipe and it is left,
Right two panels empennage is overall shaped into the first empennage and the second empennage, first installs the first empennage and the second empennage respectively, then by
One empennage and the second empennage are fixedly connected by bindiny mechanism, such as a kind of unmanned airplane empennage of notification number CN 201040583Y, because
Monolithic empennage includes shoe pipe, is L shape, still remains the problem that packaging volume is relatively large, transport is inconvenient.
Summary of the invention
In view of the above-mentioned problems, that present invention mainly solves unmanned airplane empennages is foldable, can Quick universal, and pass through shoe
The mode being connected with fuselage, solve small Package size, convenient transportation, it is easy to assembly it is quick, ensure the skill that load is effectively transmitted
Art problem.
The invention proposes a kind of foldable, fast assembling-disassembling unmanned airplane empennages, which includes left and right two sections of empennages,
Connect connection shaft, connecting pin and the nut of above-mentioned left and right two sections of empennages；Left and right two sections of empennages include empennage peace
Beam in face of fixed, the empennage stabilization back rest, empennage rudder face girder, empennage stabilization rib, the institute on the forward and backward beam of empennage stabilization
State multiple connectors and empennage shoe connector；The multiple connector includes：Beam connection before port tailplane stabilization, right tail
Wing stabilization front-axle beam front end face connector, starboard tailplane stabilization front-axle beam rear end face connector, beam connection after port tailplane stabilization,
Beam connection after starboard tailplane stabilization；Left and right two sections of empennages are linked together by above-mentioned multiple connectors；It is described
The connection of left and right two sections of empennages is realized as follows：Before being fixed with port tailplane stabilization on the front end face of port tailplane stabilization front-axle beam
Beam connection is respectively fixed with the connection of starboard tailplane stabilization front-axle beam front end face on the front and rear end of starboard tailplane stabilization front-axle beam
It is stable to be fixed with port tailplane on the front end face of the port tailplane stabilization back rest for part and starboard tailplane stabilization front-axle beam rear end face connector
Beam connection behind face is fixed with beam connection after starboard tailplane stabilization on the rear end face of the starboard tailplane stabilization back rest；Described
Be provided on each connector lower opening for install connect shaft, will connect shaft sequentially pass through these connectors from front to back along course
Lower opening after be connected and fixed to allow left and right two sections of empennages around connection shaft rotation to forming shaft with nut；It is connecting
Hole is also provided on part to be connected and fixed for empennage, after left and right two sections of empennages are rotated to proper angle, by connecting pin from
Beam connection before port tailplane stabilization, starboard tailplane stabilization front-axle beam front end face connector upper hole penetrate then connected with nut it is solid
Fixed, two sections of empennages left and right in this way are fixed and are connected by the connecting pin of top and the connection shaft of lower section respectively in junction
Securely；
Work forms inverted " V " type configuration in use, the left and right two sections of empennages of expansion, then by the socket with left and right shoe,
Realize that empennage and fuselage are linked together.
Preferably, left and right two sections of empennages are full symmetric, after left and right two sections of empennages are unfolded and fix, install in junction
Upper forward and backward radome fairing guarantees that empennage aerofoil profile is completely smooth.
Preferably, the mounting platform of antenna equipment is set in the upper covering end face of left and right two sections of empennage junctions.
Preferably, the connection of the empennage and shoe is linked together by the connection type of axis hole；Left and right two sections of empennage tails
End is equipped with the connector of pass, and shoe tail end serves as axis；After fuselage, wing and shoe connect, empennage is covered from back to front in tail
Tail end is supportted, the two is threaded into connector in side after being tightly combined and is connected and fixed, to realize that empennage passes through shoe and fuselage
It is linked together.
A kind of unmanned plane comprising fuselage, wing, left shoe, right shoe and as described above foldable, fast assembling-disassembling
Unmanned airplane empennage.
By above scheme, the unmanned plane foldable tail swing device be by left and right empennage stabilization, left and right empennage rudder face,
The composition such as multiple connectors and left and right empennage shoe connector on the left and right forward and backward beam of empennage, left and right two sections of empennages are complete
Holohedral symmetry.
The foldable tail swing device is laid out using inverted " V " type.Left and right two sections symmetrical empennages are connected in one by multiple connectors
It rises, can rotate around the axis, realize the function of empennage folding and expanding.
The foldable tail swing device is respectively provided with tubular connection piece in the tail end of left and right two sections of empennages, respectively with left and right tail
Support is connected, so that empennage and fuselage are linked together.
The left and right stabilization of the foldable empennage using twin beams more ribbed structures layout, by three hinge connectors with
Rudder face is connected.The steering engine for installing synchronous interaction respectively on two rib structures of stabilization, for controlling the deflection of rudder face.For side
Just the installation of steering engine is respectively provided with rectification lid in lower aerofoil.
The left and right rudder face of the foldable empennage is using the more ribbed structure layouts of single-beam.The rudder installed on empennage stabilization
Machine is connected by adjustable drawbar with rudder face, and control surface deflection angle is controlled；Left and right empennage rudder face passes through three hinge connectors respectively
It is connected with corresponding empennage stabilization.
The connection of the foldable empennage and shoe is linked together by axis hole connection type, the company that wherein empennage is equipped with
Fitting is that tubular serves as hole, and shoe serves as axis, and the connector on empennage packs into after shoe is tightly combined, in the side wall of connector
The two is connected and fixed by upper screw-in threaded connector, so that realizing is linked together empennage by shoe and fuselage.
The foldable empennage fixes a connector for being provided with upper and lower two hole, on the right side before port tailplane stabilization on web
Also a connector for being provided with upper and lower two hole is fixed on the front end face of empennage front-axle beam, the lower opening of this two pieces is shaft hole, and upper hole is
Left and right empennage is connected and fixed hole.A connector for being provided with a lower opening is fixed on the rear end face of starboard tailplane front-axle beam, this hole is shaft
Hole.
The foldable empennage, each fixed a connection piece, the two connectors on the rear web of left and right empennage stabilization
It is provided with a hole, this hole is also shaft hole.
The foldable empennage, the shaft hole for the connector fixed on the left and right forward and backward web of empennage stabilization is same
Axis screws in connection shaft and fixation, so that the expansion merging for left and right two sections of empennages provides rotary shaft.
The foldable empennage is opened left and right two sections of empennages, rotating around the connection shaft of junction when deployment is desired
Rotation, the covering i.e. empennage that is harmonious is expanded to design position on left and right stabilization, realizes that left and right empennage transforms into inverted " V " configuration.
The foldable empennage, after left and right two sections of empennages are threaded to designated position, adjustment makes on port tailplane stabilization front-axle beam
The upper hole for the front end face connector fixed on connector and starboard tailplane stabilization front-axle beam is coaxial, and it is solid to screw in connecting pin connection
It is fixed, to realize being connected and fixed for left and right empennage.
Finally, installing forward and backward radome fairing in junction, guarantee the complete smooth of empennage aerofoil profile.
Antenna can be arranged on the covering end face of left and right empennage junction according to actual operation requirements in the foldable empennage
Etc. equipment mounting platform, facilitate equipment to install, meet equipment arrangement and requirement.
The advantage of the invention is that：
1), the foldability of empennage makes it dramatically save packaging space, convenient transportation；
2), empennage connection connector quantity used is few, connection can be completed using conventional tool, simple installation is easy to grasp
Make, facilitate the Quick universal in outfield, there is very strong practicability.
Compared with a kind of unmanned airplane empennage of notification number CN 201040583Y, transport relatively small with Package size is more
It is convenient, substitution is connected using connector and latches connection, has many advantages, such as that mounting and adjusting is convenient, maintenance is convenient, be convenient for exchanging.
Detailed description of the invention
Fig. 1 is the schematic diagram of foldable empennage of the invention in the deployed state.
For the schematic diagram under folded state in foldable empennage of the invention, (left figure is axis side view to Fig. 2, and right figure is to face
Figure).
Fig. 3 is the topology layout figure of foldable empennage of the invention.
Fig. 4 is the stabilization of foldable empennage of the invention and the connection figure of rudder face.
Fig. 5 is the connection outline drawing of the left and right two sections of empennages of foldable empennage of the invention.
Fig. 6 is the connection structure diagram of the left and right two sections of empennages of foldable empennage of the invention.
Fig. 7 is the connection figure of foldable empennage and shoe of the invention.
Fig. 8 is outline drawing after the folding of foldable empennage of the invention.
Fig. 9 is junction detail drawing after the folding of foldable empennage of the invention.
Figure 10 is certain type unmanned plane outline drawing using the foldable empennage of the present invention.
Wherein, 1 is port tailplane, and 2 be starboard tailplane, and 3 be connection shaft, and 4 be beam connection before port tailplane stabilization, and 5 be the right side
Empennage stabilization front-axle beam front end face connector, 6 be starboard tailplane stabilization front-axle beam rear end face connector, and 7 is after port tailplane stabilizations
Beam connection, 8 be beam connection after starboard tailplane stabilization, and 9 be empennage stabilization front-axle beam, and 10 be the empennage stabilization back rest, and 11 are
Empennage rudder face girder, 12 be empennage stabilization rib, and 13 be port tailplane shoe connector, and 14 be starboard tailplane shoe connector, and 15 are
Connecting pin, 16 be nut, and 17 be left shoe, and 18 be right shoe, and 19 be antenna mounting platform, and 20 be steering engine, and 21 connect for hinge
Fitting, 22 be front fairing, and 23 be rear radome fairing.
Specific embodiment
A specific embodiment of the invention is further detailed below in conjunction with attached drawing.
A take-off weight is the vertical take-off and landing drone of 100kg, using high aspect ratio wing, double shoe empennages and V
Tail layout, tail push engine postposition.The type unmanned plane uses such foldable empennage for convenience of installing and transporting.Specifically
It realizes as follows：
The unmanned plane use inverted " V " type layout foldable empennage, tail gear be by left and right empennage stabilization, it is left and right
Empennage rudder face, the composition such as multiple connectors and left and right empennage shoe connector on the left and right forward and backward beam of empennage.Left and right two
Section empennage is full symmetric, and symmetrical two sections of empennages are connected together by connector, can be rotated around the axis and be realized folding and expanding.
The left and right stabilization of the unmanned airplane empennage uses the more ribs of single-beam using the more ribbed structure layouts of twin beams, left and right rudder face
Formula topology layout, left and right stabilization pass through three hinge connectors 21 respectively and are connected with corresponding rudder face.In two ribs of stabilization
On the steering engine 20 of synchronous interaction is installed, for convenience of the installation of steering engine, in lower aerofoil equipped with rectification lid.Institute on empennage stabilization
The steering engine of installation is connected by adjustable drawbar with rudder face, and the deflection of rudder face is controlled.
The type of attachment of left and right two sections of empennages 1,2 is as follows：Left tail is fixed on the front end face of port tailplane stabilization front-axle beam
Beam connection 4 before wing stabilization is respectively fixed with starboard tailplane stabilization front-axle beam on the front and rear end of starboard tailplane stabilization front-axle beam
Front end face connector 5 and starboard tailplane stabilization front-axle beam rear end face connector 6 are fixed on the front end face of the port tailplane stabilization back rest
Beam connection 7 after port tailplane stabilization is fixed with the connection of the starboard tailplane stabilization back rest on the rear end face of the starboard tailplane stabilization back rest
Part 8.Before port tailplane stabilization beam connection 4, be provided with upper and lower two holes on starboard tailplane stabilization front-axle beam front end face connector 5,
Beam connection 7 is connected with the starboard tailplane stabilization back rest after starboard tailplane stabilization front-axle beam rear end face connector 6, port tailplane stabilization
Lower opening is only provided on part 8.The upper hole of these connectors is used for being connected and fixed, being fixedly connected with pin 15 for left and right empennage, and lower opening is used
In being fixedly connected with shaft 3.Specific practice be will connect shaft 3 sequentially passed through from front to back along course these connectors 4,5,6,7,
It is connected and fixed to form shaft with nut 16 after 8 lower opening, left and right two sections of empennages is rotated around connection shaft 3.When
After the rotation to proper angle of left and right two sections of empennages 1,2, by connecting pin 15 from beam connection 4, starboard tailplane before port tailplane stabilization
The upper hole of stabilization front-axle beam front end face connector 5 penetrates back nut 16 and is connected and fixed, so that left and right two sections of empennages 1,2 connect
Connect fixation.
It is respectively provided with tubular empennage shoe connector 13,14 in the tail end of left and right two sections of empennages, the connection of empennage and shoe is
It is linked together by axis hole connection type, the connector 13,14 on middle left and right empennage serves as hole, and left and right shoe 17,18
Serve as corresponding axis, the connector on empennage packs into after shoe is tightly combined, and screws in threaded connector on the side wall of connector
It is connected and fixed, so that realizing is linked together empennage by shoe and fuselage.
Finally, installing forward and backward radome fairing 22,23 in junction, guarantee the complete smooth of empennage aerofoil profile.According to actually making
With requiring, it is provided with the mounting platform 19 of the equipment such as antenna on the covering end face of left and right empennage junction, equipment is facilitated to pacify
Dress also meets equipment arrangement and requirement.
Verifying, the inverted " V " type tail after expansion are used, stable configuration has high-intensitive rigidity.In practical set,
Connector quantity used is few, and installation can be completed using common tool, connects simple firm, simple installation.The structure of each component
Size reduces because of decomposition, and vanning is facilitated to be easy to transport.This empennage realizes design requirement, meets easy for installation, operation
Simply, it is connected firmly, the use demand of convenient transportation etc..
The content that description in the present invention is not described in detail belongs to the prior art well known to professional and technical personnel in the field.
The above embodiment of the present invention is the explanation to scheme and cannot be used for the limitation present invention, has protection scope comparable with the present invention
Any change in meaning and scope is all considered as including within the protection scope of the present invention.
Claims (5)
1. a kind of foldable, fast assembling-disassembling unmanned airplane empennage, which is characterized in that the empennage include left and right two sections of empennages (1,
2) connection shaft (3), connecting pin (15) and the nut (16) of above-mentioned left and right two sections of empennages (1,2), are connected；Described left and right two
Section empennage (1,2) includes empennage stabilization front-axle beam (9), the empennage stabilization back rest (10), empennage rudder face girder (11), empennage peace
Determine face rib (12), multiple connectors (4,5,6,7,8) and empennage shoe connector on the forward and backward beam of empennage stabilization
(13,14)；The multiple connector (4,5,6,7,8) includes：Beam connection (4) before port tailplane stabilization, starboard tailplane stabilization
Front-axle beam front end face connector (5), starboard tailplane stabilization front-axle beam rear end face connector (6), beam connection after port tailplane stabilization
(7), beam connection (8) after starboard tailplane stabilization；
Left and right two sections of empennages are linked together by above-mentioned multiple connectors (4,5,6,7,8)；Described left and right two sections
The connection of empennage (1,2) is realized as follows：Port tailplane stabilization front-axle beam company is fixed on the front end face of port tailplane stabilization front-axle beam
Fitting (4) is respectively fixed with starboard tailplane stabilization front-axle beam front end face connector on the front and rear end of starboard tailplane stabilization front-axle beam
(5) and starboard tailplane stabilization front-axle beam rear end face connector (6), port tailplane is fixed on the front end face of the port tailplane stabilization back rest
Beam connection (7) after stabilization, are fixed with beam connection after starboard tailplane stabilization on the rear end face of the starboard tailplane stabilization back rest
(8)；Be provided on each connector (4,5,6,7,8) lower opening for install connect shaft (3), will connection shaft (3) along navigate
It is connected and fixed to be formed and turned with nut (16) after to the lower opening for sequentially passing through these connectors (4,5,6,7,8) from front to back
Axis rotates left and right two sections of empennages around connection shaft (3)；Upper hole is also provided on connector (4,5) for empennage
It is connected and fixed, after left and right two sections of empennages (1,2) rotation to proper angle, by connecting pin (15) before port tailplane stabilization
Beam connection (4), starboard tailplane stabilization front-axle beam front end face connector (5) upper hole penetrate and then be connected and fixed with nut (16),
The connection shaft (3) of connecting pin (15) and lower section of the two sections of empennages (1,2) left and right in this way above junction passes through respectively is solid
Determine and is connected firmly；
Work forms inverted " V " type configuration in use, the left and right two sections of empennages (1,2) of expansion, then by with left and right shoe (17,
18) socket realizes that empennage and fuselage are linked together.
2. foldable, fast assembling-disassembling unmanned airplane empennage according to claim 1, which is characterized in that left and right two sections of empennages
(1,2) are full symmetric, when left and right two sections of empennages (1,2) are unfolded and after fix, junction install forward and backward radome fairing (22,
23), guarantee that empennage aerofoil profile is completely smooth.
3. foldable, fast assembling-disassembling unmanned airplane empennage according to claim 1 to 2, which is characterized in that at left and right two sections
The mounting platform (19) of the upper covering end face setting antenna equipment of empennage (1,2) junction.
4. foldable, fast assembling-disassembling unmanned airplane empennage according to claim 1 to 3, which is characterized in that the empennage and tail
The connection of support is linked together by the connection type of axis hole；Left and right two sections of empennages (1,2) tail end is equipped with the connector of pass,
Shoe tail end serves as axis；After fuselage, wing and shoe connect, empennage is covered from back to front in shoe tail end, and the two is tightly combined
It is threaded into connector in side afterwards to be connected and fixed, to realize that empennage is linked together by shoe and fuselage.
5. a kind of unmanned plane, which is characterized in that it includes fuselage, wing, left shoe (17), right shoe (18) and such as claim
Foldable, fast assembling-disassembling unmanned airplane empennage described in any one of 1-4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810464397.8A CN108860570A (en) | 2018-05-15 | 2018-05-15 | A kind of foldable, fast assembling-disassembling unmanned airplane empennage and the unmanned plane including the empennage |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810464397.8A CN108860570A (en) | 2018-05-15 | 2018-05-15 | A kind of foldable, fast assembling-disassembling unmanned airplane empennage and the unmanned plane including the empennage |
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| Publication Number | Publication Date |
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| CN108860570A true CN108860570A (en) | 2018-11-23 |
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| CN201810464397.8A Pending CN108860570A (en) | 2018-05-15 | 2018-05-15 | A kind of foldable, fast assembling-disassembling unmanned airplane empennage and the unmanned plane including the empennage |
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| CN111434579A (en) * | 2019-01-11 | 2020-07-21 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle tail boom quick assembly disassembly structure |
| CN112141319A (en) * | 2019-06-27 | 2020-12-29 | 海鹰航空通用装备有限责任公司 | M-type variable sweepback folding unmanned aerial vehicle |
| CN112429198A (en) * | 2020-11-27 | 2021-03-02 | 青岛航空技术研究院(中国科学院工程热物理研究所青岛研究中心) | Small unmanned aerial vehicle type V-shaped empennage sleeve plug-in multi-degree-of-freedom locking device |
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| CN112141319A (en) * | 2019-06-27 | 2020-12-29 | 海鹰航空通用装备有限责任公司 | M-type variable sweepback folding unmanned aerial vehicle |
| CN112141319B (en) * | 2019-06-27 | 2024-05-03 | 海鹰航空通用装备有限责任公司 | M-shaped variable sweepback folding unmanned aerial vehicle |
| CN112429198A (en) * | 2020-11-27 | 2021-03-02 | 青岛航空技术研究院(中国科学院工程热物理研究所青岛研究中心) | Small unmanned aerial vehicle type V-shaped empennage sleeve plug-in multi-degree-of-freedom locking device |
| CN115071962A (en) * | 2022-07-21 | 2022-09-20 | 峰飞航空科技(昆山)有限公司 | Unmanned aerial vehicle |
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Application publication date: 20181123 |